US6103337A - Fiber-reinforced composite materials structures and methods of making same - Google Patents

Fiber-reinforced composite materials structures and methods of making same Download PDF

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Publication number
US6103337A
US6103337A US09/112,493 US11249398A US6103337A US 6103337 A US6103337 A US 6103337A US 11249398 A US11249398 A US 11249398A US 6103337 A US6103337 A US 6103337A
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Prior art keywords
fibers
strength
preform
abutment
constituent
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US09/112,493
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English (en)
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Keith E. Burgess
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Albany International Techniweave Inc
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Albany International Techniweave Inc
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Priority to US09/112,493 priority Critical patent/US6103337A/en
Assigned to ALBANY INTERNATIONAL TECHNIWEAVE, INC. reassignment ALBANY INTERNATIONAL TECHNIWEAVE, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BURGESS, KEITH E.
Priority to CN99801120A priority patent/CN1120085C/zh
Priority to EP99956472A priority patent/EP1035969A4/fr
Priority to IL13485299A priority patent/IL134852A/xx
Priority to BR9906578-9A priority patent/BR9906578A/pt
Priority to PCT/US1999/014576 priority patent/WO2000002959A2/fr
Priority to CA002303259A priority patent/CA2303259C/fr
Priority to NZ503288A priority patent/NZ503288A/en
Priority to KR1020007002425A priority patent/KR20010023769A/ko
Priority to AU13074/00A priority patent/AU746077B2/en
Priority to JP2000559185A priority patent/JP2002538014A/ja
Priority to ZA200001011A priority patent/ZA200001011B/xx
Publication of US6103337A publication Critical patent/US6103337A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/14—Making preforms characterised by structure or composition
    • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/114—Single butt joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/001—Profiled members, e.g. beams, sections
    • B29L2031/003—Profiled members, e.g. beams, sections having a profiled transverse cross-section
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24033—Structurally defined web or sheet [e.g., overall dimension, etc.] including stitching and discrete fastener[s], coating or bond
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249923—Including interlaminar mechanical fastener

Definitions

  • reinforced composite materials to produce structural components is now widespread, particularly in applications where their desirable characteristics are sought of being light in weight, strong, tough, thermally resistant, self-supporting and adaptable to being formed and shaped.
  • Such components are used, for example, in aeronautical, aerospace, satellite, battery, recreational (as in racing boats and autos), and other applications.
  • the reinforcement component may be made from materials such as glass, carbon, ceramic, aramid (e.g., "KEVLAR"), polyethylene, and/or other materials which exhibit desired physical, thermal, chemical and/or other properties, chief among which is great strength against stress failure.
  • KEVLAR aramid
  • polyethylene polyethylene
  • the constituent reinforcement materials may be in any one or more of the following physical forms: fibers per se, monofilaments, multifilaments, yarns, twisted tow or untwisted tow or sliver produced from fibers and/or other forms of continuums.
  • reinforcement preforms may be formed into batts, arrays or other groupings, and/or they may be woven, knitted or otherwise oriented into desired configurations and shapes for reinforcement preforms.
  • Reinforcement material for use as elements in composite structures within the contemplation of this invention in all of the various compositions, forms and configurations which they may take (including, without limitation, those listed above and referred to elsewhere herein), are referred to herein as "reinforcement preforms".
  • reinforcement preforms are combined with matrix material to form desired finished components or to produce working stock for the ultimate production of finished components.
  • One of the properties frequently sought in selecting the material from which to make such reinforcement preforms forms is that of high strength.
  • a typical characteristic of materials which exhibit that property is that their highest strength by a significant margin is in the direction of the long axes of the constituent fibers or filaments.
  • a practice in fabricating such reinforcement preforms is to so orient the reinforcement preform constituent materials that their long axes are substantially in the same direction as will be the forces to which the finished components in be subjected. Since those forces may be multi-directional, in some applications the reinforcement material may be oriented multi-directionally, typically in a lamination of two or more plies, to render the strength properties of the finished component operable in more than one direction, even to the point of being quasi-isotropic.
  • Such forces may be caused to be borne primarily by fibers whose long axes are oriented in the direction those forces, thus enabling the strengthening constituents of the composite structures to present their highest load-bearing capabilities to them.
  • This principle is also followed in producing long continuums of such reinforcing materials, as in the forming of yarn, thread or other continuums, such as those used for stitching components together, and in the forming of sheets or strips which are anticipated to bear forces primarily in selected directions.
  • Such continuums in the form of a stitching thread or yarn may be made as loosely constructed tow or sliver in which the constituent fibers have been combined at a long lay length, so that the long axes of substantially the preponderance of the constituent fibers are as nearly straight as possible and are substantially parallel to the long axis of the continuum, thereby enhancing the strength bearing capabilities of the continuum in that long axis direction.
  • the preponderance of the constituent reinforcing materials in whatever form they are presented (e.g., as individual fibers, or as continuums, or as fibers in single or overlaid batts, tow, sliver, etc.), may typically be oriented substantially in the anticipated direction in which high strength characteristics are to be imparted to the reinforcing preform and the component of which it is to become a part.
  • matrix material may be introduced to and into the pre-form, so that typically the reinforcement preform becomes encased in the matrix material and matrix material fills the intersticial areas between the constituent elements of the reinforcement preform.
  • the matrix material may be any of a wide variety of materials, such as epoxy, polyester, vinyl-ester, ceramic, carbon and/or other materials, which also exhibit desired physical, thermal, chemical and/or other properties.
  • the materials chosen for use as the matrix may or may not be the same as that of the reinforcement preform and may or may not have comparable physical, chemical thermal or other properties.
  • the reinforcement preform and the matrix material may then be cured and stabilized in the same operation by thermosetting or other known per se methods, and then subjected to other operations toward producing the desired component. It is significant to note at this point that after being so cured, the then solidified masses of the matrix material normally are very strongly adhered to the reinforcing material (e.g., the reinforcement preform). As a result, stress on the finished component, particularly via its matrix material acting as an adhesive between fibers, may be effectively transferred to and borne by the constituent material of the reinforcing reinforcement preform.
  • a related consideration is to make each juncture between the constituent components as strong as possible against being pulled apart as a result of forces being applied to it. Otherwise, given the desired very high strength of the reinforcement preform constituents per se, weakness of the juncture compared to that of each of the combined elements per se becomes, effectively, a "weak link" in a structural "chain".
  • An example of this type of intersecting configuration is where one of two component elements is an elongated, flat, planar rib that is oriented substantially at right angles to and across a mid-span location of the other of the components which is in the form of a planar sheet.
  • An objective often ought in such constructions is to inhibit or totally prevent the planar sheet from deflecting objectionably or failing as pressure is applied to it in the direction of the width dimension of the reinforcing rib.
  • An second example is where the objective is simply to provide a juncture between intersecting elements (such as planar sheets per se, sheets and strips or other shapes, etc.) which will not fail upon forces being applied to one of the intersecting element in directions away from the other element which it intersects.
  • Matrix materials usually are selected primarily for having qualities such as the ability to bind reinforcing fibers to each other so as to transfer forces between the reinforcing fibers and for chemical or thermal resistance, in favor of which high strength is given low priority.
  • an objective in using the reinforcement constituent in composite materials in the first place is to enhance the strength characteristics of the composite structure far in excess of that attainable using the matrix material alone. Therefore, junctures relying on matrix material per se for their strength are insufficiently strong for this intended use.
  • the first panel is bifurcated at one end to form two divergent, co-planar panel contact surfaces in the prior art manner, that have been joined to the second panel by stitches of uncured flexible composite thread through both panels.
  • the panels and thread have then been "co-cured”: i.e., cured simultaneously.
  • the bearing flange(s) of the stiffening rib are placed in contacting juxtaposition with a the surface of the panel, and the two elements (i.e., the rib and the panel) are then joined by a fibrous "filament" or thread which is inserted vertically through the panel and into the reinforcing member, with some of the filament extending into and in line with the main body of the "stiffening flange” i.e., the portion of the stiffening rib which is vertical to the plane of the panel element.
  • the asserted effect of this is to have some of the fibers that have been introduced by the filament extend from the panel element into the stiffening flange portion of the stiffening rib. While perhaps efficacious for certain purposes, such prior art constructions still do not exhibit the desired amount of strength against failure of such joins with consequent separation of the constituent reinforced elements from each other.
  • Yet another object of this invention is to provide means for satisfying the foregoing objective in embodiments in which said reinforcement preform elements are angularly disposed with respect to each other.
  • the reinforcement preforms comprise first and second reinforcement preform elements which include strength reinforcement fibers that are in desired directional orientation.
  • the first such element has a cross-fiber surface which extends transverse of at least some its said constituent strength reinforcement fibers, which surface is in contacting juxtaposition to a selected surface region of the second element to form an abutment therebetween.
  • Abutment strength reinforcing fibers which may optionally be introduced in situ by a continuum of fibers, such as a yarn or thread, extend through at least a portion of said second element and its said selected surface region, said abutment, said cross-fiber edge surface, and into said first element substantially in the direction of orientation to some, at least, of those among its constituent strength fibers to which said cross-fiber surface is transverse.
  • FIG. 1 is a cross-sectional view of an embodiment of prior art
  • FIG. 2 is a cross-sectional of an embodiment of the present invention
  • FIG. 3 is a cross-sectional view of the embodiment of prior art shown in FIG. 1,
  • FIG. 3A is an enlargement of a portion of FIG. 3,
  • FIG. 4 is a cross-sectional view of portions of the prior art embodiment shown in FIG. 1, and
  • FIG. 5 is a cross-sectional view of another embodiment of the present invention.
  • U.S. Pat. No. 5,429,853 discloses joins between reinforced composite components in the form of a panel 2 and a strengthening rib 3.
  • the rib 3 is also based on prior art concepts in that it is made from one or two rib elements, each of which elements has been angled at about 90 degrees along its long dimension to form the rib 3 into a bearing flange 3A portion and a strengthening flange 3B portion. As such, the rib 3 may be utilized as a single such rib or, as shown in FIG.
  • FIG. 2 shows a reinforcement preform 10 for use in making fiber-reinforced composite structures. It includes as associated constituent elements, a first reinforcement preform panel 12 which is intersected in mid-span by a second reinforcement preform panel 14. As shown in FIG. 2, these elements are oriented substantially at right angles to each other.
  • juncture situations e.g., reinforcing ribs, end or center wall intersections, etc.
  • intersection angles as between joined preform elements. Particularly to be noted in FIG.
  • cross fiber-edge surface 18 which forms the contact surface of the panel 14 where it abuts the selected portion 20 of the surface of associated element 12 where the two elements 12, 14 are joined to each other by means of reinforcing fibers which are introduced into the join area by means of a thread, yarn or other continuum 16.
  • cross fiber is to be construed to mean transverse to the general direction of and intersecting fibers which have been included in a reinforcement preform for the purpose of reinforcing its strength. Although “cross fiber” may be substantially at right angles with respect to said general direction, it may vary from that orientation.
  • cross fiber surface is to be construed to mean a surface of a reinforcement preform or element thereof which extends in a "cross fiber” direction.
  • the continuum 16 may be in any of a wide variety of forms and configurations, including (without limitation) direct inserts, sequential stitches in a thread-like or yarn-like grouping of fibers (as in the form of sliver or tow), and may optionally be made from the same materials selected to be the composite reinforcing material.
  • the line of stitches may extend in the direction of the intersecting reinforcement element, since it is in this direction that the abutment itself occurs.
  • the object is to introduce reinforcing fibers, by whatever means, across the juncture between the two constituent elements of the reinforcement preform so as to impart high strength to the join between them.
  • the introduction of known per se matrix material into the intersticial portions of the reinforcement preform and around it has the effect of "gluing", or surface adhering the ends, at least, of the juncture bridging fibers to the reinforced preform elements themselves.
  • the integrity of the juncture against failure becomes primarily a function of the ability of the juncture bridging fibers which interconnect the reinforcement preform elements to withstand stress since, as previously noted, the matrix material is comparatively lacking in such strength compared to the material of the reinforcing fibers.
  • test samples were constructed substantially as disclosed in U.S. Pat. No. 5,429,853 as illustrated in FIG. 1 attached. Five more were constructed substantially in accordance with the present invention and as illustrated in FIG. 2 attached.
  • substantially identical jigs and other appliances were attached to all of samples in order to adapt them to the testing apparatus and, as nearly as possible, to isolate the test results from factors extraneous to determining the strength of the joins per se in each.
  • the samples were of substantially identical size and dimensions, and were made using identical carbon yams for reinforcing and joining, and epoxy matrix materials of substantially the same quality, dimensions and other compositional and physical properties, and the tests were conducted under substantially identical test conditions.
  • FIGS. 3 and 3A which, it will be noted, is generally the same construction as that shown in the accompanying FIG. 1, where the basic join configuration of the components is like the bifurcated junctures that are also shown in and contemplated by U.S. Pat. Nos. 4,256,790 and 4,331,495.
  • a characteristic of the embodiments illustrated in these patent references is that a radius is formed at the outside surface of the transition from the stiffening flange 3A to the bearing flange 3B (or their structural equivalents). It is created by the bearing flanges 3A bending away from the stiffening flange 3B of the element 3, in these cases, by about 90 degrees.
  • this gap is usually filled with a composite filler material that generally exhibits low stiffness, the function of which is to preclude formation in the gap of a large continuous mass of matrix material when it is introduced to the preform. Further, it is to be noted from accompanying FIGS.
  • filament 4A (which enters flange 3A at point "A", represented by line 4A-4A') has the longest gap length.
  • the gap length of filament 4B (the next longest filament), and the gap length of filament 4C (the shortest filament) are determined by their respective points of entry into the flanges 3A at points "B" and "C" respectively (represented by lines 4B-4B' and line 4C-4C' respectively). It is concluded that the comparative length of these filaments represents a significant characteristic, possibly for the following reasons.
  • the ends of the filaments, once they have been encased in matrix material that has been cured, are more or less firmly and rigidly bonded to the body of the elements 2 and 3. Their ability to stretch therefore is materially inhibited within those regions of encasement.
  • any stretching of the filaments 4A, 4B, 4C that does occur before they break will be disproportional as between the three filaments and will decrease as does the amount of their "free" length across the gap since the longer the free length, the more it can be stretched (in absolute terms) before failing.
  • a usual way of making the reinforcement preform for structures such as the flat, strip-like member from which the element 3 is formed is by a lamination of successive plies of the reinforcement material, with the fibers or yarns of each of the plies optionally being oriented more or less in one direction or oriented at angles with respect to those of the next adjacent plies.
  • the inter-laminar properties of such constructions such as their "softness” or stiffness, strength, etc., are known to be low compared to those properties in the direction indicated by the arrows "X" in FIGS. 1 and 3, which indicate the plane of orientation of the preponderance the reinforcement fibers in the element 3.
  • reinforcement fibers may be added across the join area to an extent that effectively is limited as to number only by the thickness of the butt end (cross-fiber surface) of the intersecting element.
  • the effect of each such addition will be substantially additive and cumulative with the others.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Reinforced Plastic Materials (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
US09/112,493 1998-07-09 1998-07-09 Fiber-reinforced composite materials structures and methods of making same Expired - Lifetime US6103337A (en)

Priority Applications (12)

Application Number Priority Date Filing Date Title
US09/112,493 US6103337A (en) 1998-07-09 1998-07-09 Fiber-reinforced composite materials structures and methods of making same
CA002303259A CA2303259C (fr) 1998-07-09 1999-06-28 Ameliorations nouvelles et utiles apportees a des structures en materiau composite a fibres et procede de realisation
KR1020007002425A KR20010023769A (ko) 1998-07-09 1999-06-28 섬유-보강 복합재료 구조물에 유용한 건조물 및 그 제조방법
IL13485299A IL134852A (en) 1998-07-09 1999-06-28 Fiber-reinforced composite materials structures and methods of making same
BR9906578-9A BR9906578A (pt) 1998-07-09 1999-06-28 Aperfeiçoamentos novos e úteis em estruturas de materiais compostos reforçados com fibra e método para fabricação das mesmas
PCT/US1999/014576 WO2000002959A2 (fr) 1998-07-09 1999-06-28 Ameliorations nouvelles et utiles apportees a des structures en materiau composite a fibres et procede de realisation
CN99801120A CN1120085C (zh) 1998-07-09 1999-06-28 纤维增强复合材料结构的新颖而有效的改进及其制造方法
NZ503288A NZ503288A (en) 1998-07-09 1999-06-28 New and useful improvements in fiber-reinforced composite materials structures and methods of making same
EP99956472A EP1035969A4 (fr) 1998-07-09 1999-06-28 Ameliorations nouvelles et utiles apportees a des structures en materiau composite a fibres et procede de realisation
AU13074/00A AU746077B2 (en) 1998-07-09 1999-06-28 New and useful improvements in fiber-reinforced composite materials structures and methods of making same
JP2000559185A JP2002538014A (ja) 1998-07-09 1999-06-28 繊維強化複合材料構造体及び同製作法における新規で有効な改良
ZA200001011A ZA200001011B (en) 1998-07-09 2000-02-29 New and useful improvements in fiber-reinforced composite materials structures and methods of making same.

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US (1) US6103337A (fr)
EP (1) EP1035969A4 (fr)
JP (1) JP2002538014A (fr)
KR (1) KR20010023769A (fr)
CN (1) CN1120085C (fr)
AU (1) AU746077B2 (fr)
BR (1) BR9906578A (fr)
CA (1) CA2303259C (fr)
IL (1) IL134852A (fr)
NZ (1) NZ503288A (fr)
WO (1) WO2000002959A2 (fr)
ZA (1) ZA200001011B (fr)

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US20030029545A1 (en) * 2001-01-24 2003-02-13 Lucien Fantino Method for making a carbon/carbon part
WO2003020496A1 (fr) * 2001-08-31 2003-03-13 Lockheed Martin Corporation Joint co-durci a aiguilles en z
US6555211B2 (en) * 2001-01-10 2003-04-29 Albany International Techniweave, Inc. Carbon composites with silicon based resin to inhibit oxidation
US6591197B2 (en) 2000-05-02 2003-07-08 Sikorsky Aircraft Corporation Fiber orientation verification for a composite article
US20040023581A1 (en) * 2002-08-05 2004-02-05 Bersuch Larry R. Z-pin closeout joint and method of assembly
US20060121809A1 (en) * 2004-12-08 2006-06-08 Jonathan Goering Three-dimensional woven integrally stiffened panel
US20060284337A1 (en) * 2005-06-17 2006-12-21 General Electric Company Interlaminar tensile reinforcement of SiC/SiC CMC's using fugitive fibers
US20060283014A1 (en) * 2005-06-17 2006-12-21 General Electric Company Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
US20080261474A1 (en) * 2005-11-17 2008-10-23 Jonathan Goering Hybrid Three-Dimensional Woven/Laminated Struts for Composite Structural Applications
US20090163100A1 (en) * 2007-12-21 2009-06-25 Jonathan Goering Method for Weaving Substrates with Integral Sidewalls
US20090247034A1 (en) * 2008-03-31 2009-10-01 Jonathan Goering Fiber Architecture for Pi-Preforms
US20100105269A1 (en) * 2008-10-29 2010-04-29 Jonathan Goering Pi-Shaped Preform
US20100105268A1 (en) * 2008-10-29 2010-04-29 Kenneth Ouellette Pi-Preform with Variable Width Clevis
US20100167616A1 (en) * 2008-12-30 2010-07-01 Jonathan Goering Quasi-Isotropic Three-Dimensional Preform and Method of Making Thereof
US20100167007A1 (en) * 2008-12-30 2010-07-01 Jonathan Goering Woven Preform with Integral Off Axis Stiffeners
US20110111664A1 (en) * 2009-11-11 2011-05-12 Jonathan Goering Reinforcement for darted pi preforms
WO2012138748A1 (fr) 2011-04-04 2012-10-11 Albany Engineered Composites, Inc. Ebauches de pièce de coin et leur procédé de réalisation
US20130004715A1 (en) * 2011-06-29 2013-01-03 United Technologies Corporation Reinforced composite t-joint
WO2013123029A2 (fr) 2012-02-17 2013-08-22 Albany Engineered Composites, Inc. Préforme en pi à fibres en biais
US8642151B2 (en) 2011-01-21 2014-02-04 Albany Engineered Composites, Inc. Preform and method for reinforcing woven fiber nodes
WO2015032426A1 (fr) 2013-09-04 2015-03-12 Biteam Ab Procédé et moyens pour tisser un tissu en trois dimensions, leurs articles de tissu en trois dimensions et leur utilisation
US20150251362A1 (en) * 2014-03-10 2015-09-10 Siemens Aktiengesellschaft Method and a mold for manufacturing a component for a wind turbine
EP2929999A1 (fr) 2012-10-23 2015-10-14 Albany Engineered Composites, Inc. Fabrication de raidisseurs périphériques pour enceintes de ventilateur composites
RU2573530C1 (ru) * 2014-09-02 2016-01-20 Общество с ограниченной ответственностью "Полимерные Композиционные Материалы-Алтай" Способ изготовления переходных фланцевых фитингов из армированного композиционного материала и набор оснастки для осуществления способа (варианты)
WO2017066259A1 (fr) 2015-10-13 2017-04-20 Albany Engineered Composites, Inc. Préformes tissées 3d avec canaux

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FR2934613B1 (fr) * 2008-08-01 2010-10-15 Airbus France Assemblage d'elements fibreux pour l'obtention d'une piece en materiau composite.

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Cited By (62)

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US6591197B2 (en) 2000-05-02 2003-07-08 Sikorsky Aircraft Corporation Fiber orientation verification for a composite article
US6555211B2 (en) * 2001-01-10 2003-04-29 Albany International Techniweave, Inc. Carbon composites with silicon based resin to inhibit oxidation
US20030148081A1 (en) * 2001-01-10 2003-08-07 Henry Moody Carbon composites with silicon based resin to inhibit oxidation
US6936339B2 (en) * 2001-01-10 2005-08-30 Albany International Techniweave, Inc. Carbon composites with silicon based resin to inhibit oxidation
US20030029545A1 (en) * 2001-01-24 2003-02-13 Lucien Fantino Method for making a carbon/carbon part
WO2003020496A1 (fr) * 2001-08-31 2003-03-13 Lockheed Martin Corporation Joint co-durci a aiguilles en z
US20040023581A1 (en) * 2002-08-05 2004-02-05 Bersuch Larry R. Z-pin closeout joint and method of assembly
US20060121809A1 (en) * 2004-12-08 2006-06-08 Jonathan Goering Three-dimensional woven integrally stiffened panel
US7713893B2 (en) 2004-12-08 2010-05-11 Albany Engineered Composites, Inc. Three-dimensional woven integrally stiffened panel
US20060283014A1 (en) * 2005-06-17 2006-12-21 General Electric Company Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
US7754126B2 (en) 2005-06-17 2010-07-13 General Electric Company Interlaminar tensile reinforcement of SiC/SiC CMC's using fugitive fibers
US7549840B2 (en) 2005-06-17 2009-06-23 General Electric Company Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
US20060284337A1 (en) * 2005-06-17 2006-12-21 General Electric Company Interlaminar tensile reinforcement of SiC/SiC CMC's using fugitive fibers
US20080261474A1 (en) * 2005-11-17 2008-10-23 Jonathan Goering Hybrid Three-Dimensional Woven/Laminated Struts for Composite Structural Applications
US7943535B2 (en) 2005-11-17 2011-05-17 Albany Engineered Composites, Inc. Hybrid three-dimensional woven/laminated struts for composite structural applications
US20090163100A1 (en) * 2007-12-21 2009-06-25 Jonathan Goering Method for Weaving Substrates with Integral Sidewalls
WO2009085746A1 (fr) 2007-12-21 2009-07-09 Albany Engineered Composites, Inc. Procédé de tissage de substrats avec parois laterales intégrées
US8703629B2 (en) 2007-12-21 2014-04-22 Albany Engineered Composites, Inc. Method for weaving substrates with integral sidewalls
US20110217893A1 (en) * 2007-12-21 2011-09-08 Albany Engineered Composites, Inc. Method for weaving substrates with integral sidewalls
US7964520B2 (en) 2007-12-21 2011-06-21 Albany Engineered Composites, Inc. Method for weaving substrates with integral sidewalls
US20090247034A1 (en) * 2008-03-31 2009-10-01 Jonathan Goering Fiber Architecture for Pi-Preforms
US7712488B2 (en) 2008-03-31 2010-05-11 Albany Engineered Composites, Inc. Fiber architecture for Pi-preforms
US8127802B2 (en) 2008-10-29 2012-03-06 Albany Engineered Composites, Inc. Pi-preform with variable width clevis
US20100105269A1 (en) * 2008-10-29 2010-04-29 Jonathan Goering Pi-Shaped Preform
US8079387B2 (en) 2008-10-29 2011-12-20 Albany Engineered Composites, Inc. Pi-shaped preform
US20100105268A1 (en) * 2008-10-29 2010-04-29 Kenneth Ouellette Pi-Preform with Variable Width Clevis
WO2010078053A1 (fr) 2008-12-30 2010-07-08 Albany Engineered Composites, Inc. Préforme tridimensionnelle quasi isotrope et son procédé de fabrication
US20100167007A1 (en) * 2008-12-30 2010-07-01 Jonathan Goering Woven Preform with Integral Off Axis Stiffeners
US20100167616A1 (en) * 2008-12-30 2010-07-01 Jonathan Goering Quasi-Isotropic Three-Dimensional Preform and Method of Making Thereof
WO2010078157A2 (fr) 2008-12-30 2010-07-08 Albany Engineered Composites, Inc. Ébauche tissée avec raidisseurs désaxés intégrés
US8859083B2 (en) 2008-12-30 2014-10-14 Albany Engineered Composites, Inc. Quasi-isotropic three-dimensional preform and method of making thereof
US8846553B2 (en) 2008-12-30 2014-09-30 Albany Engineered Composites, Inc. Woven preform with integral off axis stiffeners
US20110111664A1 (en) * 2009-11-11 2011-05-12 Jonathan Goering Reinforcement for darted pi preforms
WO2011059922A1 (fr) 2009-11-11 2011-05-19 Albany Engineered Composites, Inc. Renforcement pour préformes en pi à pointe, préformes en pi comprenant ce renforcement et procédé de renforcement des préformes en pi
US8389424B2 (en) 2009-11-11 2013-03-05 Albany Engineered Composites, Inc. Reinforcement for darted Pi preforms
US8642151B2 (en) 2011-01-21 2014-02-04 Albany Engineered Composites, Inc. Preform and method for reinforcing woven fiber nodes
US9132603B2 (en) 2011-01-21 2015-09-15 Albany Engineered Composites, Inc. Perform and method for reinforcing woven fiber nodes
US9757803B2 (en) 2011-01-21 2017-09-12 Albany Engineered Composites, Inc. Preform and method for reinforcing woven fiber nodes
US9205494B2 (en) 2011-01-21 2015-12-08 Albany Engineered Composites, Inc. Preform and method for reinforcing woven fiber nodes
US8663776B2 (en) 2011-04-04 2014-03-04 Albany Engineered Composites Corner fitting preforms and method of making thereof
WO2012138748A1 (fr) 2011-04-04 2012-10-11 Albany Engineered Composites, Inc. Ebauches de pièce de coin et leur procédé de réalisation
US20130004715A1 (en) * 2011-06-29 2013-01-03 United Technologies Corporation Reinforced composite t-joint
US9604389B2 (en) 2012-02-17 2017-03-28 Albany Engineered Composites, Inc. Pi-shaped preform with bias fibers
WO2013123029A2 (fr) 2012-02-17 2013-08-22 Albany Engineered Composites, Inc. Préforme en pi à fibres en biais
EP2939812A1 (fr) 2012-10-23 2015-11-04 Albany Engineered Composites, Inc. Raidisseurs périphériques pour enceintes de ventilateur composites
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US10052796B2 (en) 2012-10-23 2018-08-21 Albany Engineered Composites, Inc. Circumferential stiffeners for composite fancases
EP2929999A1 (fr) 2012-10-23 2015-10-14 Albany Engineered Composites, Inc. Fabrication de raidisseurs périphériques pour enceintes de ventilateur composites
US11485048B2 (en) 2012-10-23 2022-11-01 Albany Engineered Composites, Inc. Circumferential stiffeners for composite fancases
US10150229B2 (en) 2012-10-23 2018-12-11 Albany Engineered Composites, Inc. Circumferential stiffeners for composite fancases
EP2937198A1 (fr) 2012-10-23 2015-10-28 Albany Engineered Composites, Inc. Raidisseurs périphériques pour enceintes de ventilateur composites
US9833930B2 (en) 2012-10-23 2017-12-05 Albany Engineered Composites, Inc. Circumferential stiffeners for composite fancases
US10016913B2 (en) 2012-10-23 2018-07-10 Albany Engineered Composites, Inc. Circumferential stiffeners for composite fancases
US20160201234A1 (en) * 2013-09-04 2016-07-14 Biteam Ab Method and means for weaving, 3d fabric items thereof and their use
WO2015032426A1 (fr) 2013-09-04 2015-03-12 Biteam Ab Procédé et moyens pour tisser un tissu en trois dimensions, leurs articles de tissu en trois dimensions et leur utilisation
US9926651B2 (en) * 2013-09-04 2018-03-27 Biteam Ab Method and means for weaving, 3D fabric items thereof and their use
US20150251362A1 (en) * 2014-03-10 2015-09-10 Siemens Aktiengesellschaft Method and a mold for manufacturing a component for a wind turbine
US10086570B2 (en) * 2014-03-10 2018-10-02 Siemens Aktiengesellschaft Method and a mold for manufacturing a component for a wind turbine
US10730251B2 (en) * 2014-03-10 2020-08-04 Siemens Gamesa Renewable Energy A/S Mold for manufacturing a component for a wind turbine
RU2573530C1 (ru) * 2014-09-02 2016-01-20 Общество с ограниченной ответственностью "Полимерные Композиционные Материалы-Алтай" Способ изготовления переходных фланцевых фитингов из армированного композиционного материала и набор оснастки для осуществления способа (варианты)
US10023981B2 (en) 2015-10-13 2018-07-17 Albany Engineered Composites, Inc. 3D woven preforms with channels
WO2017066259A1 (fr) 2015-10-13 2017-04-20 Albany Engineered Composites, Inc. Préformes tissées 3d avec canaux

Also Published As

Publication number Publication date
AU1307400A (en) 2000-02-01
JP2002538014A (ja) 2002-11-12
CA2303259A1 (fr) 2000-01-20
WO2000002959A2 (fr) 2000-01-20
CN1120085C (zh) 2003-09-03
EP1035969A2 (fr) 2000-09-20
AU746077B2 (en) 2002-04-11
KR20010023769A (ko) 2001-03-26
CN1273549A (zh) 2000-11-15
IL134852A (en) 2003-02-12
IL134852A0 (en) 2001-05-20
WO2000002959A9 (fr) 2000-10-26
EP1035969A4 (fr) 2001-01-03
CA2303259C (fr) 2004-01-27
ZA200001011B (en) 2000-10-16
BR9906578A (pt) 2000-11-21
WO2000002959A3 (fr) 2000-03-23
NZ503288A (en) 2001-10-26

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